CN206841718U

CN206841718U - A kind of twenty formula layout unmanned plane

Info

Publication number: CN206841718U
Application number: CN201720275100.4U
Authority: CN
Inventors: 王长有
Original assignee: Sichuan Tengdun Technology Co Ltd
Current assignee: Sichuan Tengdun Technology Co Ltd
Priority date: 2017-03-21
Filing date: 2017-03-21
Publication date: 2018-01-05
Anticipated expiration: 2027-03-21

Abstract

The utility model discloses a kind of twenty formula layout unmanned plane, it is desirable to provide and it is a kind of that there is larger mounting space, it is easy to carry the unmanned plane of large-sized object.The technical solution adopted in the utility model is such：Including 2 fuselages, the 1 slave wing, 2 secondary vertical fins and 1 secondary horizontal tail；Wing is overlapped on the top of 2 fuselages；2 secondary vertical fins are located at 2 fuselage rears respectively, are connected with back body；The left and right ends of the horizontal tail are connected respectively with 2 secondary vertical fins or the rear end with 2 fuselages is connected respectively.

Description

A kind of twenty formula layout unmanned plane

Technical field

A kind of unmanned plane structure is the utility model is related to, particularly a kind of unmanned plane of twenty formula layout.

Background technology

Development of UAV is very fast in recent years, a kind of large-scale unmanned plane, such as predator's unmanned plane, pterosaur unmanned plane, coloured silk The unmanned plane of rainbow 4 and heron unmanned plane etc., its endurance length, can carry multiple-task load and weapon, perform multiple-task, so as to deep Favored by various countries user.

But for some large-scale mission payloads, large aerospace weapon, or need to launch in the air other larger fly Row device, still lack the unmanned plane that can be carried at present.

Utility model content

Goal of the invention of the present utility model is：For above-mentioned problem, there is provided a kind of unmanned plane of twenty formula layout, With larger mounting space, it is easy to carry large-sized object.

The technical solution adopted in the utility model is such：

Including 2 fuselages, the 1 slave wing, 2 secondary vertical fins and 1 secondary horizontal tail；

Wing is overlapped on the top of 2 fuselages；

2 secondary vertical fins are respectively above 2 afterbodies；

The left and right ends of the horizontal tail are connected respectively with 2 secondary vertical fins or the tail inner side with 2 fuselages is connected respectively.

Further, the length of the wing is more than or equal to 12 meters, and aspect ratio is more than or equal to 10.

Further, the span distance of the full machine plane of symmetry of each fuselage centre-to-centre spacing is the 20%~40% of the length of wing half.

Further, in addition to 2 propeller power set, the head of 2 fuselages is separately mounted to, or be separately mounted to 2 The afterbody of individual fuselage.

Further, the power set of quantity such as it is fixed with below the wing of two fuselage outer sides.

Further, power set are fixedly arranged above in the wing of two inboards.

Further, the horizontal tail is arranged on the upper end of left and right vertical fin.

In summary, by adopting the above-described technical solution, the beneficial effects of the utility model are：

1st, high aspect ratio wing, twin fuselage, twin vertical fin, horizontal tail etc. are joined together to form " twenty " formula gas by the utility model Dynamic layout.The layout has closed frame structure, and integral rigidity is high, and structural stability is strong；The pneumatic of course can also be reduced simultaneously Elastic deformation, lift course stability.

The 2nd, bearing point can be set on the wing of the utility model or so inboard, be easy to carry mission payload cabin, Cargo hold, or large-scale mission payload, large aerospace weapon are directly carried, or other aircraft.Further, it is also possible to it is described nobody Machine or so fuselage is respectively arranged on aerial array, or even wing and horizontal tail and also arranges aerial array, flat as air-borne early warning detection Platform.Therefore, the utility model is well suited as aerial unmanned delivery's platform, reconnaissance and surveillance platform or scientific experimentation platform.

Brief description of the drawings

Fig. 1 is the schematic diagram of the utility model embodiment 1；

Fig. 2 is the top view of the utility model embodiment 1；

Fig. 3 is the schematic diagram of the utility model embodiment 2；

Fig. 4 is the schematic diagram of the utility model embodiment 3；

Fig. 5 is the schematic diagram of the utility model embodiment 4；

Fig. 6 is the schematic diagram of the utility model embodiment 5；

Fig. 7 is the schematic diagram of the utility model embodiment 6；

Fig. 8 is that the utility model carries schematic diagram.

Marked in figure：1 is wing；2 be fuselage；3 be vertical fin；4 be horizontal tail；5 be power set；6th, 7 be undercarriage；8 are Large-scale mission payload；11 be aileron；12 be wing flap；13 be flaperon；31 be rudder；41 be elevator.

Embodiment

Below in conjunction with the accompanying drawings, the utility model is described in detail.

In order that the purpose of this utility model, technical scheme and advantage are more clearly understood, below in conjunction with accompanying drawing and implementation Example, the utility model is further elaborated.It should be appreciated that specific embodiment described herein is only explaining The utility model, it is not used to limit the utility model.

Embodiment 1

Fig. 1 is the schematic diagram of the utility model embodiment 1, and the unmanned plane of the present embodiment includes the 1 slave wing 1；2 fuselages 2, point Not An Zhuan the lower section of wing 1 left and right sides；2 secondary vertical fins 3, are separately mounted to the rear end of left and right fuselage 2；1 secondary horizontal tail 4, installed in a left side The upper end of right vertical fin 3, the left and right ends of horizontal tail 4 are connected with the 2 secondary upper ends of vertical fin 3 respectively；2 secondary propellers 5 are located at left and right fuselage 2 respectively Front end, be connected to by rotating shaft on the engine being arranged in the head of left and right fuselage 2.

Wherein, wing 1 is divided into port wing and starboard wing again from the angle of aerodynamic arrangement, and this is the normal of correlative technology field Know；2 fuselages 2 divide for left and right part, and left fuselage is identical with right fuselage theory profile or symmetrical on the full machine plane of symmetry, only Local form is because equipment installation, protrusion and blow vent etc. are it is possible that different；2 secondary vertical fins 3 divide for left and right part, left secondary vertical fin Identical with right secondary vertical fin theory profile or symmetrical on the full machine plane of symmetry, only local form is because of equipment installation, protrusion It is with blow vent etc. it is possible that different.

The aileron 11 for roll guidance is disposed with wing 1, can further arrange that wing flap 12 is used to increase during landing Lift, and flaperon 13 is added to be used to increase lift and roll guidance during landing；It is disposed with vertical fin 3 for directional control Rudder 31；The elevator 41 for pitch control is disposed with horizontal tail 4.

Fig. 2 is the top view of the utility model embodiment 1, and whole unmanned plane structure seems form Chinese from top view " twenty " word, therefore it is named " twenty " formula aerodynamic arrangement.Fig. 2 furthermore present fuselage and opened up with wing to relative position relation；It is preferred that , the span distance Y of the full machine plane of symmetry of fuselage centre-to-centre spacing is the 20%~40% of the length l/2 of wing half.

The aspect ratio of wing is preferably, equal to or greater than 10.Aspect ratio is defined as the ratio between wing span and mean geometric chord, Conventional below equation represents：

AR=l/b=l²/S；

Here l is wingspan length, and b is geometric chord of airfoil, and S is wing area.Therefore it can also state as the span (wing Length) square divided by wing area.

Embodiment 2

Fig. 3 is the schematic diagram of the utility model embodiment 2, and compared with Example 1, the horizontal tail 4 of embodiment 2 is arranged on fuselage 2 On, the left and right ends of horizontal tail 4 are connected with the tail inner side of fuselage 2.

Embodiment 3

Fig. 4 is the schematic diagram of the utility model embodiment 3, and compared with Example 1,2 secondary propellers 5 of embodiment 3 distinguish position In the rear end of left and right fuselage 2, it is connected to by rotating shaft on the engine being arranged in the afterbody of left and right fuselage 2.

Embodiment 4

Fig. 5 is the schematic diagram of the utility model embodiment 4, and compared with Example 1, embodiment 4 employs 4 jet power dresses 5 (such as fanjets, turbojet engine) are put, each installation 2 below the wing 1 in the outside of left and right fuselage 2；Optionally, root Varying number power set can be used according to needs, wherein identical quantity can be installed below the wing 1 in the outside of left and right fuselage 2 Power set, such as each installation 1, or each installation 2, or each installation 3, etc..As the deformation of the present embodiment, jet is moved Power apparatus can also replace with propeller power set.

Embodiment 5

Fig. 6 is the schematic diagram of the utility model embodiment 5, and compared with Example 1, embodiment 5 employs 2 jet power dresses 5 (such as fanjets, turbojet engine) are put, above the wing 1 of the inner side of left and right fuselage 2；Optionally, as needed Varying number power set can be used, wherein, it can be arranged on the inner side of left and right fuselage 2 by some or all of as the case may be The top of wing 1.As the deformation of the present embodiment, jet power unit can also replace with propeller power set.

Embodiment 6

Fig. 7 is the schematic diagram of the utility model embodiment 6, compared with Example 1, is installed on the root of the vertical fin 3 of the rear end of fuselage 2 Portion is protruded under the afterbody of fuselage 2.Optionally, vertical fin can also have certain camber angle or leaning angle.

Application Example

Fig. 8 is that the utility model carries schematic diagram, and mission payload or gondola 8 are lifted under the wing 1 of the inner side of left and right fuselage 2 Side.Fig. 8 illustrates the arrangement signal of undercarriage simultaneously, is arranged with nose-gear 6 and rear undercarriage 7 on left and right fuselage 2, rises and falls Frame can be fixed, or deployable and collapsible.

Preferred embodiment of the present utility model is the foregoing is only, it is all at this not to limit the utility model All any modification, equivalent and improvement made within the spirit and principle of utility model etc., should be included in the utility model Protection domain within.

Claims

1. a kind of twenty formula layout unmanned plane, it is characterised in that including 2 fuselages, the 1 slave wing, 2 secondary vertical fins and 1 secondary horizontal tail；

Wing is overlapped on the top of 2 fuselages；

2 secondary vertical fins are respectively above 2 afterbodies；

The left and right ends of the horizontal tail are connected respectively with 2 secondary vertical fins or the tail inner side with 2 fuselages is connected respectively；

And the length of the wing is more than or equal to 12 meters, aspect ratio is more than or equal to 10.

A kind of 2. twenty formula layout unmanned plane according to claim 1, it is characterised in that each full machine plane of symmetry of fuselage centre-to-centre spacing Span distance be the length of wing half 20%~40%.

3. a kind of twenty formula layout unmanned plane according to claim 1 or 2, it is characterised in that also including 2 propeller power Device, is separately mounted to the head of 2 fuselages, or is separately mounted to the afterbody of 2 fuselages.

4. a kind of twenty formula layout unmanned plane according to claim 1 or 2, it is characterised in that in the wing of two fuselage outer sides Lower section such as is fixed with the power set of quantity.

5. a kind of twenty formula layout unmanned plane according to claim 1 or 2, it is characterised in that in the wing of two inboards It is fixedly arranged above power set.

6. a kind of twenty formula layout unmanned plane according to claim 1 or 2, it is characterised in that the horizontal tail is arranged on left and right The upper end of vertical fin.

7. a kind of twenty formula layout unmanned plane according to claim 3, it is characterised in that the horizontal tail is arranged on left and right hang down The upper end of tail.

8. a kind of twenty formula layout unmanned plane according to claim 4, it is characterised in that the horizontal tail is arranged on left and right hang down The upper end of tail.

9. a kind of twenty formula layout unmanned plane according to claim 5, it is characterised in that the horizontal tail is arranged on left and right hang down The upper end of tail.